EP2565400B1

EP2565400B1 - Exhaust gas duct for a gas turbine with heat resistant liner and gas turbine having such a gas duct

Info

Publication number: EP2565400B1
Application number: EP12180128.6A
Authority: EP
Inventors: Marc Rauch; Tobias Steffen; Joachim Krautzig; Armin Busekros; Jürgen Pacholleck
Original assignee: Ansaldo Energia IP UK Ltd
Current assignee: Ansaldo Energia IP UK Ltd
Priority date: 2011-09-05
Filing date: 2012-08-10
Publication date: 2020-07-15
Anticipated expiration: 2032-08-10
Also published as: CH705514A1; US9212567B2; US20130055725A1; EP2565400A3; RU2012137773A; RU2551709C2; EP2565400A2

Description

TECHNICAL FIELD

The present invention relates to the field of gas turbine technology. It refers to a gas duct for a gas turbine according to the preamble of claim 1. The invention also refers to a gas turbine having such a gas duct.

BACKGROUND OF THE INVENTION

The present invention relates to gas turbines, especially to stationary industrial gas turbines, as are reproduced in Fig. 1 in a perspective, partially sectioned view. Fig. 1 shows a gas turbine 10 of the GT26 type of the applicant. Combustion air is inducted in this gas turbine 10 by a compressor 12 via an air intake 11, and compressed, and fed into a first combustion chamber 13 for combusting a fuel. Arranged downstream of the first combustion chamber 13 is a first (high-pressure) turbine 14 which is driven by the hot gases from the first combustion chamber 13. Provided downstream of the first turbine 14 is a second combustion chamber 15 in which a fuel is combusted together with the residual oxygen which is present in the hot gases. The hot exhaust gases from the second combustion chamber 15 drive a second (low-pressure) turbine 16 before they are discharged via a gas duct 17 to the outside or (in a combined cycle power plant) discharged into a subsequent heat recovery steam generator.
The gas duct 17 comprises a (basically cylindrical) inner casing 19 which usually serves for accommodating the exhaust gas-side rotor bearing and is enclosed concentrically and at a distance by an outer casing 18. Both casings 18 and 19 are interconnected by means of radial support struts 20 which are arranged in a distributed manner over the circumference. Through the gas duct 17, the hot exhaust gases are discharged from the gas turbine 10. For protection against the hot exhaust gases, the outer casing 18, the inner casing 19 and the support struts 20 are provided in each case with a lining or covering.
In the past, according to Fig. 2, different preformed parts were welded together to form in each case a top half 21a and a bottom half 21b of the gas duct 17'. The two halves 21a and 21b were then fastened via brackets on the support structure of the exhaust-gas housing and after being joined together were welded in the parting plane by means of welded joints 22 in order to achieve a closed flow duct.
As a result of this type of construction and assembly, various problems or disadvantages arose, however:

1. A susceptibility to cracks in the gas duct, specifically created by
1. a. stress accumulation, namely
  1. i. large inherent stresses of the gas duct as a result of the welding, and
  2. ii. high thermal stresses;
2. b. severe vibrations in combination with low natural frequencies of the gas duct;
2. poor scope for maintenance and repair.

Proposed in printed publication US 4,920,742 for gas turbines is a support structure for supporting a segmented flow-path lining, which comprises a support bracket which is connected to a frame section and has a support device which is connected to the flow-path lining, wherein the support bracket is provided with a clearance hole in order to ensure a freely floating connection for free acceptance of axial and circumferentially occurring thermal expansion and contraction of the flow-path lining. The segmentation, however, is limited to the concentric regions of the flow-path lining and does not extend to the support struts and is comparatively coarse so that thermal stresses still constitute a problem and the scope for maintenance and repair is limited. Document US 4 369 016 discloses a gas duct of the state of the art according to the preamble of claim 1.
Other solutions are disclosed in document US6041590 , US6102610 and US5363643 .

SUMMARY OF THE INVENTION

It is therefore an object of the invention to create a gas duct of the type referred to in the introduction, which avoids the disadvantages of known solutions and is distinguished by a greatly improved accessibility with maximum avoidance of thermal stresses at the same time.
This and other objects are achieved by the sum total of the features of claim 1. The invention is based on a gas duct for a gas turbine, which gas duct is formed by a concentric inner casing and an outer casing which concentrically encompasses the inner casing at a distance, and through which the exhaust gases from the gas turbine discharge to the outside, wherein the inner casing and the outer casing are interconnected by means of a multiplicity of radial support struts, and wherein the support struts, the outer casing and the inner casing are equipped in each case with a heat-resistant lining for protection against the hot exhaust gases.
The invention is also based on the fact that the linings of the support struts of the outer casing and of the inner casing are divided in each case into a plurality of separate segments which are fastened on a support structure in such a way that an individual entirely stress-free, or almost stress-free, thermal expansion of the individual segments in an expansion plane is possible.
One embodiment of the invention is characterized in that the segments are detachably fastened on the support structure.
In the present invention the segments are fixed relative to the support structure at at least one fastening point and are fastened in a freely thermally expandable manner in the expansion plane at other fastening points.
In the present invention the segments are fastened in a freely thermally expandable manner in the expansion plane relative to the support structure at all the fastening points.
In the present invention the support structure comprises a multiplicity of mountings in the region of the outer casing and the inner casing, upon which mountings the associated segments are fastened by screws.
The mountings preferably have a multiplicity of threaded holes, and the segments are fixed on the mountings by means of screws which are screwed into the threaded holes from the outside through corresponding holes in the segments.
It is also conceivable, however, that the mountings have a multiplicity of stud bolts which extend through corresponding holes in the segments, and that the segments are fastened on the stud bolts by means of corresponding clamping nuts. This type of fastening has advantages especially in more demanding regions of application (higher temperatures etc.).
The mountings especially extend in this case parallel to each other in the axial direction.
In the present invention the mountings are fastened on a concentric shell by means of radial supports.
A further embodiment of the invention is characterized in that the mountings are circumferentially spaced apart by such a distance that a segment is fastened in each case on two adjacent mountings and extends circumferentially between two adjacent mountings.
The gas turbine according to the invention, having an exhaust-side gas duct through which the exhaust gases discharge from the gas turbine to the outside, is characterized in that the gas duct is a gas duct according to the invention.

BRIEF EXPLANATION OF THE FIGURES

The invention shall subsequently be explained in more detail based on exemplary embodiments in conjunction with the drawing. In the drawing

Fig. 1: shows in a perspective, partially sectioned view an industrial gas turbine with sequential combustion, as is suitable for implementation of the invention;
Fig. 2: shows a previously known art of the assembly of a gas duct for a gas turbine according to Fig. 1;
Fig. 3: shows in a perspective view a detail of a gas duct according to an exemplary embodiment of the invention;
Fig. 4: shows another view of the gas duct from Fig. 3;
Fig. 5: shows an enlarged detail of the gas duct from Fig. 3;
Fig. 6: shows a detail of the inner support structure of the gas duct from Fig. 3;
Fig. 7: shows the top half of a support structure according to a further exemplary embodiment of the invention; and
Fig. 8: shows a fastening of the segments on the support structure from Fig. 7 by means of stud bolts and clamping nuts according to another exemplary embodiment of the invention.

WAYS OF IMPLEMENTING THE INVENTION

According to the present invention, the exhaust-side gas duct of a gas turbine is to be divided into a multiplicity of independent segments. These segments are fastened on a mounting structure. The gas duct is generally to be segmented in three regions. These three regions are the outer casing 18, the inner casing 19 and the support struts 20. The individual segments comprise correspondingly formed metal sheets which (via the mounting structure) are fastened on a support structure, lying thereunder, of the gas duct. This fastening is designed so that the completely stress-free, or almost stress-free, thermal expansion of the individual metal sheets is ensured in all operating states.
The mounting structure for the segments or metal sheets themselves is fastened on an inner or outer shell of the support structure. This fastening is also designed so that an entirely stress-free, or almost stress-free, thermal expansion in an expansion plane is possible. The number of connecting points to the support structure results from its size and from the loads which occur.
The segments are attached in a positionally fixed manner in relation to the support structure either at one (not necessarily central) point and from there can thermally expand in an entirely stress-free, or almost stress-free, manner in the expansion plane at the other fastening points, or they have the necessary clearance in the expansion plane at all the fastening points and can freely move within the constructionally necessary limits.
Fig. 3 shows in a perspective view a detail of a gas duct 17 according to an exemplary embodiment of the invention. To be seen are the outer casing 18, the inner casing 19 with corresponding segments 19a and a support strut 20 with corresponding segments 20a. Fig. 4 shows this exemplary embodiment from another viewing angle so that in this case the segments 18a of the outer casing 18 are also visible.
In Fig. 5 and Fig. 6, the mounting structure for the segments 19a of the inner casing 19 can be seen (the mounting structure on the outer casing is correspondingly constructed). This mounting structure comprises mountings 19b which are arranged in a distributed manner around the circumference, extend parallel to each other in the axial direction, and on their outer side are provided with threaded holes 24. By their one end the mountings 19b bear against a ring 19e which - as with the inner shell 19d - is part of the support structure of the inner casing 19. Instead of the ring, separate supports 19c can also be provided according to Fig. 7. On the other side, the mountings 19b are supported on the inner shell 19d at a distance by means of supports 19c.
As is seen clearly in Fig. 5, the segments 19a are detachably fastened on the mountings 19b by means of screws 23 which are screwed into the threaded holes 24 in the mountings 19b. Each segment 19a extends in this case between adjacent mountings 19b and is screwed to these mountings in each case. As a result of this type of construction, on the one hand easy accessibility to all parts of the gas duct 17 is ensured. On the other hand, as a result of the extensive segmenting of the lining of the duct thermal stresses are reduced or completely avoided.
It is also conceivable, however, and advantageous especially in the case of more demanding regions of application, if according to Fig. 8 the mountings 19b are provided with perpendicularly projecting stud bolts 25 which extend through corresponding holes in the segments 19a. The segments 19a are then fastened on the stud bolts 25 by means of clamping nuts 26.

LIST OF DESIGNATIONS

10: Gas turbine
11: Air intake
12: Compressor
13, 15: Combustion chamber
14, 16: Turbine
17, 17': Gas duct
18: Outer casing
18a: Segment (outer casing)
19: Inner casing
19a: Segment (inner casing)
19b: Mounting (inner casing)
19c: Support (inner casing)
19d: Inner shell
19e: Ring
20: Support strut
20a: Segment (support strut)
21a, b: Gas duct halves
22: Welded joint
23: Screw
24: Threaded hole
25: Stud bolt
26: Clamping nut

Claims

A gas duct (17) for a gas turbine (10), which gas duct (17) is formed by a concentric inner casing (19) and an outer casing (18) which concentrically encompasses the inner casing (19) at a distance, and through which the exhaust gases from the gas turbine (10) discharge to the outside, wherein the inner casing (19) and the outer casing (18) are interconnected by means of a multiplicity of radial support struts (20), and wherein the support struts (20), the outer casing (18) and the inner casing (19) are equipped in each case with a heat-resistant lining (18a or 19a or 20a) for protection against the hot exhaust gases,
wherein the linings of the support struts (20), of the outer casing (18) and of the inner casing (19) are divided in each case into a plurality of separate segments (18a, 19a, 20a) which are fastened on a support structure (19b - d); wherein the segments (18a, 19a, 20a) are fixed relative to the support structure (19b - d) at at least one fastening point and are fastened in a freely thermally expandable manner in the expansion plane at other fastening points or are fastened in a freely thermally expandable manner in the expansion plane relative to the support structure (19b - d) at all the fastening points, whereby an individual entirely stress-free, or almost stress-free, thermal expansion of the individual segments in an expansion plane is possible;
the gas duct being characterized in that the support structure (19b - d) comprises a multiplicity of mountings (19b) in the region of the outer casing (18) and the inner casing (19), upon which mountings the associated segments (18a, 19a) are fastened by screws an in that the mountings (19b) are fastened on a concentric shell (19d) by means of radial supports (19c).
The gas duct as claimed in claim 1, characterized in that the segments (18a, 19a, 20a) are detachably fastened on the support structure (19b - d).
The gas duct as claimed in claim 1, characterized in that the mountings (19b) have a multiplicity of threaded holes (24), and in that the segments (18a, 19a) are fastened on the mountings (19b) by means of screws (23) which are screwed into the threaded holes (24) from the outside through corresponding holes in the segments (18a, 19a).
The gas duct as claimed in claim 1, characterized in that the mountings (19b) have a multiplicity of stud bolts (25) which extend through corresponding holes in the segments (18a, 19a), and in that the segments (18a, 19a) are fastened on the stud bolts (25) by means of corresponding clamping nuts (26).
The gas duct as claimed in claim 1, characterized in that the mountings (19b) extend parallel to each other in the axial direction.
The gas duct as claimed in claim 1, characterized in that the mountings (19b) are circumferentially spaced apart by such a distance that a segment (18a, 19a) is fastened in each case on two adjacent mountings and extends circumferentially between two adjacent mountings.
A gas turbine (10) having an exhaust-side gas duct (17), through which the exhaust gases discharge from the gas turbine (10) to the outside, characterized in that the gas duct (17) is a gas duct as claimed in one of claims 1 - 6.